FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 63-100 AIRFOIL (fx63100-il) Reynolds number: 500,000 Max Cl/Cd: 121.72 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx63100-il-500000.txt Download as CSV file: xf-fx63100-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-100 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2731 0.09464 0.09253 -0.0358 1.0000 0.0243
-9.500 -0.2800 0.09099 0.08891 -0.0360 1.0000 0.0253
-9.250 -0.2934 0.08614 0.08410 -0.0381 0.9997 0.0260
-9.000 -0.2870 0.08026 0.07823 -0.0426 0.9981 0.0260
-8.750 -0.2847 0.07343 0.07141 -0.0461 0.9962 0.0265
-8.500 -0.2688 0.07007 0.06804 -0.0482 0.9945 0.0270
-8.250 -0.2572 0.06601 0.06399 -0.0512 0.9917 0.0274
-8.000 -0.2454 0.06163 0.05961 -0.0549 0.9883 0.0281
-7.750 -0.3540 0.04497 0.04262 -0.0923 0.9799 0.0214
-7.500 -0.3183 0.02607 0.02250 -0.1167 0.9735 0.0189
-7.250 -0.2810 0.02054 0.01619 -0.1227 0.9700 0.0198
-7.000 -0.2456 0.01834 0.01354 -0.1254 0.9658 0.0207
-6.750 -0.2091 0.01654 0.01156 -0.1283 0.9632 0.0221
-6.500 -0.1720 0.01598 0.01095 -0.1306 0.9611 0.0236
-6.250 -0.1370 0.01500 0.00978 -0.1323 0.9573 0.0252
-6.000 -0.1034 0.01362 0.00822 -0.1338 0.9521 0.0269
-5.750 -0.0669 0.01295 0.00754 -0.1358 0.9489 0.0289
-5.500 -0.0282 0.01253 0.00705 -0.1381 0.9463 0.0316
-5.250 0.0050 0.01152 0.00597 -0.1395 0.9389 0.0343
-5.000 0.0430 0.01102 0.00545 -0.1417 0.9342 0.0372
-4.750 0.0789 0.01073 0.00509 -0.1433 0.9275 0.0401
-4.500 0.1167 0.00990 0.00422 -0.1456 0.9207 0.0440
-4.250 0.1515 0.00960 0.00388 -0.1470 0.9120 0.0478
-3.750 0.2183 0.00891 0.00304 -0.1493 0.8900 0.0565
-3.500 0.2482 0.00876 0.00281 -0.1495 0.8776 0.0613
-3.250 0.2785 0.00850 0.00253 -0.1500 0.8670 0.0726
-3.000 0.3088 0.00825 0.00230 -0.1505 0.8575 0.0957
-2.750 0.3381 0.00802 0.00213 -0.1508 0.8477 0.1258
-2.500 0.3698 0.00741 0.00196 -0.1522 0.8391 0.2754
-2.250 0.3991 0.00720 0.00194 -0.1525 0.8296 0.3645
-2.000 0.4280 0.00712 0.00191 -0.1527 0.8208 0.4040
-1.750 0.4569 0.00705 0.00188 -0.1528 0.8120 0.4386
-1.500 0.4856 0.00695 0.00191 -0.1529 0.8029 0.4862
-1.000 0.5423 0.00696 0.00204 -0.1528 0.7852 0.5784
-0.750 0.5705 0.00703 0.00207 -0.1527 0.7768 0.6009
-0.500 0.5986 0.00707 0.00210 -0.1525 0.7676 0.6169
-0.250 0.6265 0.00711 0.00214 -0.1523 0.7587 0.6336
0.000 0.6544 0.00717 0.00218 -0.1521 0.7497 0.6493
0.250 0.6822 0.00721 0.00223 -0.1520 0.7403 0.6618
0.500 0.7099 0.00728 0.00228 -0.1517 0.7311 0.6761
0.750 0.7372 0.00733 0.00233 -0.1514 0.7197 0.6889
1.000 0.7644 0.00739 0.00238 -0.1511 0.7058 0.6991
1.250 0.7916 0.00746 0.00242 -0.1507 0.6915 0.7095
1.500 0.8187 0.00753 0.00248 -0.1504 0.6789 0.7186
1.750 0.8461 0.00761 0.00256 -0.1502 0.6672 0.7282
2.000 0.8732 0.00771 0.00264 -0.1499 0.6540 0.7384
2.250 0.8999 0.00780 0.00272 -0.1495 0.6389 0.7487
2.500 0.9266 0.00790 0.00282 -0.1491 0.6230 0.7598
2.750 0.9532 0.00802 0.00293 -0.1487 0.6055 0.7717
3.000 0.9790 0.00816 0.00304 -0.1482 0.5832 0.7841
3.250 1.0043 0.00833 0.00316 -0.1476 0.5564 0.7983
3.500 1.0291 0.00854 0.00332 -0.1468 0.5276 0.8151
3.750 1.0530 0.00875 0.00349 -0.1460 0.4996 0.8359
4.250 1.0918 0.00897 0.00376 -0.1421 0.4508 1.0000
4.500 1.1178 0.00934 0.00401 -0.1418 0.4243 1.0000
4.750 1.1430 0.00976 0.00429 -0.1414 0.3934 1.0000
5.000 1.1678 0.01020 0.00458 -0.1410 0.3588 1.0000
5.250 1.1916 0.01073 0.00492 -0.1404 0.3172 1.0000
5.500 1.2143 0.01138 0.00533 -0.1396 0.2706 1.0000
5.750 1.2365 0.01209 0.00580 -0.1388 0.2280 1.0000
6.000 1.2590 0.01276 0.00629 -0.1381 0.1933 1.0000
6.250 1.2811 0.01347 0.00682 -0.1373 0.1595 1.0000
6.750 1.3216 0.01524 0.00812 -0.1351 0.0831 1.0000
7.000 1.3420 0.01609 0.00885 -0.1340 0.0646 1.0000
7.250 1.3631 0.01684 0.00955 -0.1329 0.0550 1.0000
7.500 1.3857 0.01737 0.01012 -0.1321 0.0507 1.0000
7.750 1.4069 0.01802 0.01077 -0.1310 0.0470 1.0000
8.000 1.4264 0.01883 0.01161 -0.1297 0.0439 1.0000
8.250 1.4478 0.01939 0.01224 -0.1287 0.0421 1.0000
8.500 1.4681 0.02003 0.01293 -0.1276 0.0401 1.0000
8.750 1.4865 0.02082 0.01373 -0.1262 0.0381 1.0000
9.000 1.4983 0.02213 0.01511 -0.1238 0.0358 1.0000
9.250 1.5173 0.02274 0.01581 -0.1225 0.0347 1.0000
9.500 1.5335 0.02348 0.01663 -0.1207 0.0334 1.0000
9.750 1.5468 0.02429 0.01750 -0.1185 0.0320 1.0000
10.000 1.5580 0.02521 0.01846 -0.1161 0.0305 1.0000
10.250 1.5608 0.02679 0.02010 -0.1127 0.0290 1.0000
10.500 1.5683 0.02812 0.02154 -0.1100 0.0278 1.0000
10.750 1.5812 0.02901 0.02254 -0.1082 0.0268 1.0000
11.000 1.5918 0.03011 0.02373 -0.1062 0.0255 1.0000
11.250 1.6015 0.03130 0.02498 -0.1043 0.0244 1.0000
11.500 1.6073 0.03289 0.02662 -0.1022 0.0233 1.0000
11.750 1.6040 0.03560 0.02942 -0.0994 0.0222 1.0000
12.000 1.6165 0.03665 0.03060 -0.0982 0.0213 1.0000
12.250 1.6258 0.03809 0.03215 -0.0969 0.0203 1.0000
12.500 1.6334 0.03975 0.03391 -0.0956 0.0194 1.0000
12.750 1.6400 0.04156 0.03579 -0.0944 0.0187 1.0000
13.000 1.6424 0.04392 0.03821 -0.0932 0.0180 1.0000
13.250 1.6371 0.04739 0.04179 -0.0918 0.0173 1.0000
13.500 1.6424 0.04964 0.04418 -0.0911 0.0169 1.0000
13.750 1.6458 0.05218 0.04687 -0.0905 0.0163 1.0000
14.000 1.6482 0.05491 0.04973 -0.0901 0.0157 1.0000
14.250 1.6505 0.05772 0.05264 -0.0899 0.0152 1.0000
14.500 1.6516 0.06078 0.05579 -0.0899 0.0147 1.0000
14.750 1.6515 0.06409 0.05919 -0.0902 0.0143 1.0000
15.000 1.6464 0.06828 0.06349 -0.0906 0.0139 1.0000
15.250 1.6344 0.07368 0.06903 -0.0913 0.0136 1.0000
15.500 1.6319 0.07787 0.07339 -0.0923 0.0133 1.0000
15.750 1.6268 0.08259 0.07828 -0.0935 0.0131 1.0000
16.000 1.6206 0.08769 0.08355 -0.0951 0.0128 1.0000
16.250 1.6131 0.09313 0.08916 -0.0970 0.0126 1.0000
16.500 1.6050 0.09885 0.09503 -0.0993 0.0123 1.0000
16.750 1.5964 0.10480 0.10114 -0.1019 0.0121 1.0000
17.000 1.5884 0.11082 0.10731 -0.1047 0.0119 1.0000
17.250 1.5786 0.11730 0.11394 -0.1079 0.0118 1.0000
17.500 1.5688 0.12391 0.12069 -0.1115 0.0116 1.0000
17.750 1.5598 0.13048 0.12739 -0.1152 0.0114 1.0000
18.000 1.5504 0.13724 0.13428 -0.1191 0.0113 1.0000
18.250 1.5415 0.14400 0.14116 -0.1233 0.0112 1.0000
18.500 1.5278 0.15202 0.14934 -0.1284 0.0111 1.0000
18.750 1.5189 0.15904 0.15647 -0.1330 0.0110 1.0000
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